Commonwealth legislation

AD/CESSNA 185/2 Amdt 4 - Rear Spar

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

Requires immediate modification of the rear spar root on Cessna 185 agricultural aeroplanes (except those with specified rear-spar part numbers) and recurring inspections of the rear-spar web and upper flange for fatigue cracks using at least 4X magnification or an approved device. Modified aeroplanes inspect every 500 hours; unmodified aeroplanes inspect every 100 hours. The rule affects aircraft owners/operators, who must carry out structural work, regular inspections, and remove a trailing-edge root rib for detailed checks when access is doubtful.

JSON API

Deep dive

Want the full deep dive?

Zoe can write the in-depth analysis on top of the summary above: how it works, who it affects and what each part actually does.

Current sections

Direct links to the current provisions in AD/CESSNA 185/2 Amdt 4 - Rear Spar.

AD/CESSNA 185/2 Amdt 4 - Rear Spar

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

View image in the official source
Cessna 185 Series Aeroplanes

AD/CESSNA 185/2

Amdt 4

Rear Spar 12/74

Applicability: All models except those with rear spars P/Nos. 0523400-90 LH and -91 RH; 0523400-111 LH and -112 RH.

Requirement: 1. Modify the rear spar root, left and right mainplanes on all agricultural aeroplanes in accordance with Rex Aviation Drawing RA-491 or an alternative scheme approved by the Secretary.

2. Inspect the mainplane rear spar web for fatigue cracks in the root area. These cracks originate in the radius which is located under the attachment fittings. This inspection shall be carried out using a magnifying glass of at least 4X magnification or alternatively a device such as the “Syte Ade” may be employed.

3. Inspect the upper flange of the rear spar channel at the outer end of the attachment fitting. This can be done via the flap bay inner inspection panel.

4. Since the trailing edge root end fits closely to the spar, it may be difficult to detect possible cracks, therefore where doubt exists, the trailing edge root end rib shall be removed for more detailed inspection.

Note: The affected area is illustrated in Rex Aviation Technical Memorandum No. 12 dated 10 May 1960.

Compliance: For Para 1: Forthwith.

For Paras 2 and 3: Aeroplanes modified to Rex Aviation Drawing RA-491 - at intervals not exceeding 500 hours time in service. All other aeroplanes - at intervals not exceeding 100 hours time in service.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

1 AD/CESSNA 185/2 Amdt 4 - Rear Spar